Aviation device for storing liquefied gas with collector

Abstract

An aviation cryogenic tank arrangement for storing gas, having a spherical or annular shape about an axis, comprising: an inner container (26) defining a liquefied gas storage chamber (28); a housing (27) comprising an inner container (26); an insulating chamber (29) defined between the inner container (26) and the housing (27), the reduced-pressure insulating chamber (29) having a tightness equal to or superior to 10-9 mbar * L / sec; a removable collector (38) passing through the housing (27) and the inner container (26) in a sealed manner, the collector (38) extending through the diameter or diagonal of the inner container (26) and having a free end proximate the bottom of the inner container (26); and a conduit supplied by the collector (38).

Description

[0001] The present invention relates to the field of aviation.

[0002] Since the beginning of aviation, it has used high-octane gasoline engines. After 1945, the development of jet engines and turbines led to the use of kerosene, which has a higher molecular weight than gasoline and is less flammable. These fuels are stored in tanks located in the wings, at the fuselage-wing junction, or in the tail.

[0003] The trend towards reducing CO2 gas emissions results in engines that consume less. However, as certain technologies mature, especially increasing blade tip speeds, the CO2 gas emissions gains are diminishing. There seems to be a growing need for a breakthrough.

[0004] Therefore, gas aircraft projects emerged. Combustion of gases with short or non-existent carbon chains with oxygen produces little or no pollution. On the other hand, storage of H2, O2 or C1 or C2 gases is difficult due to the small size of gas molecules and there is a risk of leakage.

[0005] On the ground, these gases are typically stored in pressurized containers that are too heavy, bulky, and contain too much potential pressure energy to be carried on an aircraft, or in welded and / or bonded cryogenic tanks. These gases have a limited cryogenic shelf life, proportional to the volume stored.

[0006] Furthermore, hydrogen, methane, ethane, ethylene, acetylene or oxygen stored in liquid form cannot be used by internal or external combustion engines or fuel cells. Final consumption requires the gaseous state.

[0007] The need to store propellant gas in the aircraft and extract it from the storage for onboard consumption, while using aviation maintenance technology and avoiding the need for new standardization. This is because the development of new standards is a long and time-consuming process, which risks delaying the marketing of gas-powered aircraft. Acquiring new maintenance knowledge is also long and expensive, and may even lead to silence.

[0008] The present invention proposes an aviation cryogenic storage tank device for storing gas, which has a generally elongated shape, with rounded ends, in particular a spherical or annular shape around an axis, comprising an inner container defining a liquefied gas storage chamber, an outer shell accommodating the inner container, and an insulating chamber defined between the inner container and the outer shell, wherein the sealing performance of the decompression insulating chamber is equal to or better than 10 -9 mbar*l / s, a detachable collector passes through the outer shell and the inner container in a sealed manner, the collector extends on the diameter or diagonal of the inner container and has a free end close to the bottom of the inner container, and a conduit provided by the collector. According to the present invention, the cryogenic storage tank meets the requirements of low mass and compactness. The cryogenic storage tank can supply flammable liquids or fuels in the form of liquefied gas.

[0009] In one embodiment, the device includes a thermally insulating flexible neck that forms a sealed interface between the collector on the one hand and the outer shell and inner container on the other hand, the neck being disposed around a portion of the collector, the neck passing through the insulating chamber so that the collector can be removed independently of the pressure in the insulating chamber. The collector is easily removed and reinstalled for quick maintenance.

[0010] In one embodiment, the device includes a thermal plug assembly that is removably mounted on the collector and accessible from the outside. Easy maintenance.

[0011] In one embodiment, the device comprises a support ring mounted between the inner container and the outer shell. The structure is strong.

[0012] In one embodiment, the device comprises a connection including an axial recess in the outer shell for receiving and supporting an axial projection of the inner container, and a housing supporting the outer shell and surrounding the connection. The connection accommodates expansion that may occur.

[0013] In one embodiment, the neck has an outer surface with an annular herringbone shape. High sealing performance.

[0014] In one embodiment, the neck has a wavy outer surface. The conductive path is extended.

[0015] In one embodiment, the housing comprises a bottom plate, a sealing panel and a gasket for bearing the pressure between the bottom plate and the panel and / or between the panels, wherein the bottom plate comprises ribs and longitudinal members. The structure is simple and repairable.

[0016] In one embodiment, the device comprises an anti-sway member within the inner container.The mechanical properties of the device, in particular the stability, are improved.

[0017] In one embodiment, the device comprises reinforcing ribs, preferably struts or tie rods, within the inner container. The device, in particular the inner container, can be reduced in weight and increased in rigidity.

[0018] In one embodiment, a hydrogen absorbing material is disposed in the insulating chamber. A low pressure is maintained in the insulating chamber.

[0019] In one embodiment, a detector for detecting the presence of hydrogen is installed in the insulating chamber. An alarm may be sounded if a limit value is exceeded.

[0020] In one embodiment, the assembly comprises a device as described above, a temporary storage tank forming a gasification component for increasing the pressure of the gas supplied by the device, an upstream valve designed to open for the flow of liquid during the phase of filling the temporary storage tank and closed outside the filling phase, a downstream valve designed to open for the flow of gas during the phase of emptying the temporary storage tank and closed outside the emptying phase, the upstream valve and the downstream valve being closed during the gasification phase, the upstream valve and the downstream valve having an all-or-nothing control, and a compressor arranged downstream of the downstream valve, said compressor being activated at the end of the emptying phase to make the pressure value in the temporary storage tank lower than the pressure value in the device, and a pressure reducing valve arranged downstream of the downstream valve, said pressure reducing valve being activated at the beginning of the emptying phase to make the pressure value of the gas present lower than the pressure value in the temporary storage tank. The device provides the necessary autonomy for the aircraft through the volume in the temporary storage tank, regardless of the state of the device. The temporary storage tank can be designed for a gas pressure of several hundred bars, but still provide the selected gas pressure for the consumable components. The valve is reliable. The temporary storage tank can be fully emptied, thereby increasing the amount of gas available to the consumable components and making the pressure of the temporary storage tank lower than the normal pressure in the device at the end of the emptying. The temporary storage tank is filled by operating the cryogenic valve under the action of the pressure difference. Eliminating the cryogenic pump saves quality and reduces the risk of accidents.

[0021] In one embodiment, the temporary storage tank is designed for a service pressure higher than 500 bar.

[0022] In one embodiment, the device is designed for a service pressure of less than 8 bar.

[0023] Other features and advantages of the present invention will become apparent from a reading of the following detailed description and the accompanying drawings, in which:

[0024] [ Figure 1 ] schematically shows an axial cross-sectional view of a device according to one aspect of the present invention.

[0025] [ Figure 2 ] schematically shows a cross-section of an apparatus according to one aspect of the present invention.

[0026] [ Figure 3 ] schematically shows an exploded side view of an apparatus according to one aspect of the present invention.

[0027] [ Figure 4 ] schematically shows an exploded side view of an apparatus according to another aspect of the present invention.

[0028] [ Figure 5 ] schematically shows a perspective view of an apparatus according to another aspect of the present invention.

[0029] [ Figure 6] schematically shows a cross-section of a neck according to one aspect of the present invention.

[0030] [ Figure 7 ] schematically shows a cross-section of a neck and collector according to one aspect of the present invention.

[0031] [ Figure 8 ] schematically shows a perspective view of a component according to one aspect of the present invention.

[0032] [ Fig. 9 ] schematically shows a cross-section of a neck and collector according to another aspect of the present invention.

[0033] [ Fig.10 ] schematically shows a cross-section of a neck and collector according to another aspect of the present invention.

[0034] The drawings may be used not only to supplement the invention but also, where applicable, to help define the invention.

[0035] Aviation gas storage units are designed for transport by aircraft: airplanes, drones, helicopters, etc. In other words, the gas is stored in liquid form in cryogenic tanks at extremely low temperatures. Cryogenic tanks cannot withstand high pressures, especially pressures greater than 10 bar.

[0036] The stored gas is selected from the group consisting of hydrogen, methane, ethane, ethylene, acetylene and oxygen.

[0037] Applicants also intend to take into account that vaporization is a rapid phenomenon even in an ambient atmosphere of -55°C at high altitudes. For example, gaseous hydrogen at 0°C and 1 atmosphere is about 800 times less dense than liquid hydrogen at -253°C, and therefore has about 800 times the volume.

[0038] In addition, aviation maintenance rules require that most parts of an aircraft can be removed and repaired or replaced. This allows the aircraft to land anywhere - an airport for airplanes, a landing zone for helicopters - that is suitable for its weight and landing requirements, but does not provide maintenance equipment specific to the aircraft model. If damage is detected, the aircraft is designed to be permanently or temporarily repaired, or disassembled to replace or repair the faulty part, in accordance with the manufacturer's manual and documents approved by the aviation safety authorities. It is desirable that the part be easily accessible to the maintenance operator. If it is to be replaced, it is desirable that the part be as small as possible to facilitate handling and transportation. If repair is required, it is best to be able to repair the part using tools and methods commonly used and proven in the aviation industry.

[0039] Aircraft are inspected daily, weekly, etc., and the length of time an aircraft is grounded is inversely proportional to the frequency.

[0040] However, gas tanks used in terrestrial industry or in space are not subject to such requirements and in particular are not designed for such repairability.

[0041] The applicant has identified a need for an aircraft cryogenic tank capable of carrying a flammable liquid for storage, particularly hydrogen, methane, ethane, ethylene, acetylene or oxygen, and capable of supplying the tank outlet.

[0042] The applicant has identified a need for a removable aviation cryogenic tank that can be inspected according to the aircraft inspection mode and is repairable. In addition, a tank is sought that has a high useful volume / external volume ratio and a high mass / total mass ratio of the gas contained therein, with high reliability and safety.

[0043] As shown, the aviation gas storage device has a generally elongated shape with rounded ends. The aviation gas storage device may be in the form of a ring around a longitudinal axis. The aviation gas storage device includes an outer shell and an inner container. The inner container forms a liquefied gas storage chamber. The inner container is contained in the outer shell. Generally, the inner container and the outer shell are spaced relatively far apart from each other.

[0044] In the embodiment shown, the aviation gas storage device has a central portion of a rotational cylinder and hemispherical ends. However, exceptional forms having cylindrical, annular and / or hemispherical shapes can be manufactured.

[0045] Each cryogenic tank is insulated to contain liquid fuel or oxidant at -253° C. Each cryogenic tank is capable of withstanding a maximum operating pressure of approximately 6 to 10 bar.

[0046] exist Figures 1 to 3 In the embodiment shown, the cryogenic tank 2 has an elongated shape, in particular an elongated shape around an axis. The cryogenic tank 2 has a domed end portion and a substantially cylindrical central portion. In a variant, the cryogenic tank 2 has a spherical shape.

[0047] The cryogenic tank 2 comprises an inner container 26 and an outer shell 27. The inner container 26 defines a liquefied gas storage chamber 28 for accommodating a gas load at a liquefaction temperature and a boil-off gas upper end. The inner container 26 is gas-tight. The inner container 26 can withstand the liquefaction temperature, for example -253°C for hydrogen. The outer shell 27 contains the inner container 26. The outer shell 27 is made of a plurality of removable parts so that the inner container 26 can be accessed. The outer shell 27 protects the inner container 26 from impacts. The outer shell 27 provides structural strength for the aviation gas storage device. The outer shell 27 is made of a material that can withstand temperatures below -60°C to at least +80°C.

[0048] Between the inner container 26 and the outer shell 27, an insulating chamber 29 is defined. The insulation of the insulating chamber 29 is provided by a pressure reduced compared to the atmospheric pressure. In addition, a solid insulating material may be provided in the insulating chamber 29. The reduced pressure insulating chamber 29 has a pressure equal to or better than 10 -9 Helium impermeability of mbar*l / s is defined between the inner container 26 and the outer shell 27. The airtightness of the insulating chamber 29 includes airtightness relative to the inside of the inner container 26 and airtightness relative to the external atmosphere.

[0049] The inner container 26 may be made of a welded metal alloy. Examples of metal alloys may be Al-Cu-Li, in particular 2050 or 2099, Al-Cu, in particular 2219, stainless steel, in particular 304, 304L, 316, 316L. The inner container 26 has an elongated shape with two domed ends surrounding the body. The body may be cylindrical. The body may be rotating.

[0050] The housing 27 includes a chassis 30, an airtight panel 31, and a gasket for bearing the pressure between the chassis 30 and the panel 31 and / or between the panels 31. The panel 31 may be assembled on the chassis 30 by screws.

[0051] The chassis 30 includes ribs 32 and longitudinal members 33. The ribs 32 may have a closed profile, such as a ring. The longitudinal members 33 extend longitudinally. The longitudinal members 33 are connected at the ends of the housing 27.

[0052] The housing 27 includes an assembly of panels 31. The panels 31 are made of a welded metal alloy or a composite material. Examples of composite materials may be epoxy resin with carbon fiber, Kevlar fiber and / or glass fiber. Examples of metal alloys may be Al-Mg, particularly 5086, Al-Mg-Si, particularly 6061, Al-Cu-Li, particularly 2195.

[0053] Between the panel 31 and the chassis 30, a gasket is provided. The gasket may be metal / metal or made of a synthetic material, such as an elastomer. In the case where the gasket is made of a synthetic material, a groove is provided in the panel 31 or the chassis 30 to accommodate the gasket. In the free state, the height of the gasket protruding from the groove is less than 10% of the height of the gasket. The height refers to the diameter of the O-ring seal.

[0054] The cryogenic tank 2 comprises two connections between the outer shell 27 and the inner container 26 to support the inner container 26. The connection gaskets are configured for very low thermal conductivity.

[0055] At least one of the connections is of the sliding type, so that the differential expansion of the outer shell 27 and the inner container 26 can be accommodated. The connections are carried by the outer shell 27. The first connection is located at the end. The end connection 34 may include a central protrusion at one end of the inner container 26, which cooperates with the axial concave surface of the outer shell 27 to form a raised housing, which slides axially over a travel of a few millimeters, so that the contraction of the inner container 26 when filled with liquefied gas and the expansion of the inner container 26 after emptying of liquefied gas are free. The end connection 34 is configured to have a very long heat conduction path.

[0056] The second connection is located at a distance from the end opposite to the first connection. The second connection surrounds the inner container 26. The second connection is installed in the insulating chamber 29. The second connection includes a support ring 35. The support ring 35 is installed between the inner container 26 and the outer shell 27. The support ring 35 is installed in the insulating chamber 29 at a distance from the connection.

[0057] The support ring 35 comprises an outer sector 36 protruding radially outwards. The outer sector 36 has a peripheral surface in contact with the bore of the housing 27. The outer sector 36 occupies an angle of approximately 15° to 40°.

[0058] The support ring 35 comprises inner sectors 37 protruding radially inwards. There are three inner sectors 37 here. The inner sectors 37 have a convex surface, which contacts the periphery of the inner container 26. The inner sectors 37 occupy an angle of about 15° to 40°. The outer sectors 36 and the inner sectors 37 alternate. The outer sectors 36 and the inner sectors 37 are angularly spaced from each other. Preferably, the angle between the three inner sectors 37 and the three outer sectors 36 is about 20° to 30°, they are distributed alternately, separated by areas without protrusions, and each occupy an angle of about 40° to 30°. The support ring 35 is held on the inner container 26 by sufficient friction or by permanent fixing.

[0059] The support ring 35 is made of a composite material having low thermal conductivity and high mechanical strength.

[0060] The cryogenic storage tank 2 includes a removable collector 38 that sealably passes through the outer shell 27 and the inner container 26. The collector 38 includes a straight pipe 39 for taking out the liquefied gas in the inner container 26. The straight pipe 39 is made of an insulating material. The collector 38 includes a first opening inside the inner container 26. The collector 38 includes a second opening outside the outer shell 27. The second end is designed to be connected to a conduit, such as an outlet conduit 4, see Figure 6. The first end and the second end are connected by a hole. In the installed state, the first end is located near the bottom of the inner container 26. The first end is free. Therefore, the collector 38 extracts the liquefied gas. When the liquid level is low, the extraction stops. In other words, in operation, the inner container 26 contains a gas phase and a liquid phase. At the end of filling, the liquid phase is the largest and the gas phase is the smallest. At the end of extraction, the liquid phase is the smallest or even does not exist, and the gas phase is the largest. The liquid phase is extracted. Extracting the liquid phase allows the use of pipes with significantly smaller diameters relative to the gas phase. The compactness of the components downstream of the cryogenic tank 2 is improved. Pipe 39 is also used to fill the liquefied gas.

[0061] The collector 38 comprises at a second end a plug 41 surrounding the tube 39. The plug 41 is made of an insulating material. The plug 41 protrudes outside the housing 27. The plug 41 may have a gripping area for removal, for example during maintenance. The outer diameter of the plug 41 is greater than the diameter of the tube 39. The plug 41 forms a removable gas-tight head of the cryogenic tank 2.

[0062] The stop assembly comprises a stop plug 41 and a stop cap 45. In the case of an aircraft or drone type device, the cryogenic tank 2 can be mounted with the stop towards the front of the device and the free end of the tube 39 towards the rear of the device, to take advantage of the general inclination of the device by a few degrees, thereby allowing a more complete filling of the liquefied gas and a more complete extraction of the liquefied gas. The cryogenic tank 2 can also be mounted at an inclination, in particular by having unequal height support members between the front and rear of the cryogenic tank 2.

[0063] In addition, the collector 38 includes a level gauge 40. The level gauge 40 extends along the tube 39. The level gauge 40 is connected to the outside of the tank by a cable communication passing through a plug 41. The level gauge 40 provides a signal representing the liquid level as an output. The level gauge can be capacitive. The smaller the angle of the collector 38 relative to the horizontal plane, the higher the accuracy of the level gauge. This is because, for a given level gauge resolution and a given height of the internal container 26, an increase in the length of the internal container 26 allows the length of the level gauge to be increased, and therefore the accuracy to be increased. For example, a level gauge at 30° relative to the horizontal plane has twice the accuracy compared to a vertical level gauge.

[0064] The collector 38 includes a gas vent 53 for rapid discharge in the event of overpressure. The vent 53 is also used to vent gas during filling to avoid overpressure. The vent 53 is used for re-pressurization by introducing gas during extraction (if necessary). The vent 53 is provided in the plug 41 and emerges in the inner container 26 near the plug 41. The vent 53 is provided with a liquid check valve.

[0065] The exhaust port 53 is provided in the plug 41 and emerges in the inner container 26 near the plug 41. Thus, the exhaust port 53 is connected to the gas upper end of the inner container 26. The exhaust port 53 is connected to a pipe passing through the plug 41. A valve having an opening pressure lower than the pressure allowed by the cryogenic tank 2 can be connected to the pipe. A rupture disc having a rupture pressure lower than the pressure allowed by the cryogenic tank 2 can be connected to the pipe. The valve and the rupture disc are installed in parallel.

[0066] The collector 38 comprises a temperature sensor which is arranged at the bottom of the inner plug 41. The temperature sensor provides information on the temperature measured in the inner container 26.

[0067] The cryogenic storage tank 2 includes an insulating neck 42. The neck 42 has a hole. The neck 42 can be made of metal. The metal should be selected to have low thermal conductivity, high mechanical strength, good flexibility and hydrogen impermeability. The neck 42 is welded or screwed to the inner container 26 with a gasket. The neck 42 is welded or screwed to the outer shell 27 with a gasket. The neck 42 has sufficient flexibility to accommodate the expansion difference between the inner container and the outer shell 27. The neck 42 includes an outer wall fixed to the inner container 26 and the outer shell 27. The neck 42 includes an inner wall away from the inner container 26 and the outer shell 27. The inner wall can be fixed to the outer wall at the end of the neck 42.

[0068] The outer wall is tubular. The inner wall is tubular in the form of a bellows. The inner wall may be made of a metal plate having a thickness less than that of the outer wall to increase the elastic deformation capability. The inner wall may have a bellows shape, which increases the applicability of the elastic deformation. The bellows shape, such as a wave shape, reduces the contact surface between the inner wall and the plug 41, resulting in low heat conduction.

[0069] Advantageously, the bellows-type inner wall comprises two concentric metal sheets. The metal sheets fit together and are connected at the ends. This forms a double wall, thereby reducing the risk of leakage. If one of the two metal sheets is pierced, it can be detected by applying a gas pressure between the two sheets that is higher than the pressure in the insulating chamber and lower than the atmospheric pressure and monitoring the change in the applied pressure. If the applied pressure decreases, the metal sheet with the larger diameter leaks with the insulating chamber. If the applied pressure increases, the metal sheet with the smaller diameter leaks with the hole in the neck 42. The neck can then be replaced. In addition, if only one metal sheet leaks, the insulating chamber maintains its low pressure, ensuring low thermal conduction, and the cryogenic storage tank 2 can operate until the next maintenance operation. If a single metal sheet loses its seal, the insulating chamber will lose its low thermal conductivity and the cryogenic storage tank 2 will be urgently emptied due to the loss of the contents.

[0070] The neck 42 forms an airtight interface with the collector 34 on the one hand and with the outer shell 27 and the inner container 26 on the other hand. The neck 42 maintains the airtightness between the outer shell 37 and the inner container 26 regardless of the position of the collector 38 or even in the absence of the collector 38. The neck 42 is sealingly attached in a perforation provided in the outer shell 27. The neck 42 is sealingly attached in a perforation provided in the inner container 26. The perforation in the outer shell 27 and the perforation in the inner container 26 are located at one of the circular ends of the cryogenic tank 2, near the outer diameter of the top cryogenic tank 2. The outer end of the collector 38 extends to the outside of the neck 42. The collector 38 extends to the outside of the neck 42, toward the interior of the cryogenic tank 2, and downward to the other circular end of the cryogenic tank 2.

[0071] The neck 42 is arranged around a portion of the collector 38. The neck 42 passes through the insulating chamber 29 so that the collector 38 can be removed independently of the pressure in the insulating chamber 29. The neck 42 is provided with a through hole 43, in which the plug 41 of the collector 38 is detachably mounted. The contact surface between the neck 42 and the plug 41 may be provided with a concave annular tooth set 44 to increase the length of the leakage path and facilitate the mechanical retention of the collector 38 in the neck. Here the tooth set 44 has a herringbone shape. The plug 41 has a smooth rotating outer surface in a free state. The plug 41 fits the neck 42. A small gap may be provided between the bellows and the plug 41. A liquid guide plate is provided inside the neck near the storage chamber 28. The plug 41 is made of a heat-insulating material. The plug 41 may include a solid outer shell and an insulating synthetic foam located inside the outer shell.

[0072] exist Figure 6 and Figure 7 In an embodiment of the present invention, the neck 42 is welded to the inner container 26 around its outer wall. The neck 42 has a flange that is superimposed on the flange of the inner container 26. The welding can be performed by an electron beam directed at the flange. The neck 42 is welded to the outer shell 27 around its outer wall at a distance from the weld point to the inner container 26. The outer wall of the neck 42 includes two different and independent parts, one connected to the inner container 26 and the other connected to the outer shell 27.

[0073] The inner wall connects the two parts of the outer wall. The inner wall comprises two concentric metal sheets with a thickness between 0.1 mm and 0.2 mm. Outwardly, the neck 42 comprises a collar 54 directed toward the inner wall. The collar 54 connects the inner wall and the outer wall sealingly. A gasket 55 is attached to the collar 54, in particular by screwing. The gasket 55 is in contact with the plug 41 of the collector 38. There is no level gauge here.

[0074] The cryogenic tank 2 comprises a cover 45 permanently mounted on the collector 38 and accessible from the outside. The cover 45 is fixed to the tube 39 by screws or bolts. The cover 45 is arranged outside the housing 27. The cover 45 is arranged at said outer end of the collector 38. The cover 45 is gas-tight.

[0075] The design service pressure of the cryogenic storage tank 2 is less than 8 bar, in particular 6 bar.

[0076] Advantageously, the cryogenic tank 2 includes an anti-sway member mounted inside the inner container 26. The anti-sway member includes one or more perforated plates that divide the inner volume of the inner container 26 into several areas. The surface area of ​​the holes in the perforated plates can be about 1% to 5% of the surface area of ​​the perforated plates. The perforated plates can be longitudinal or transverse. The perforated plates reduce the movement speed of the liquefied gas in the inner container 26 during acceleration (for example, during takeoff or landing or during atmospheric turbulence).

[0077] Advantageously, the cryogenic tank 2 comprises reinforcing ribs located inside the inner container 26. The reinforcing ribs comprise at least one strut or tie rod connecting opposite areas of the inner container 26. The reinforcing ribs make it possible to lighten the rest of the structure of the inner container 26.

[0078] In the insulating chamber 29, a hydrogen absorbing material 46, such as a nanoporous material, is installed. In the event of a slight leak, the insulation loss associated with the pressure increase in the insulating chamber 29 is reduced. After such a leak occurs, the housing 27 is disassembled to open the insulating chamber 29, and the hydrogen absorbing material 46 is removed to desorb the hydrogen, such as by heating.

[0079] A hydrogen presence detector 47 is installed in the insulating chamber 29 to monitor the presence of hydrogen. If the leak is severe, emergency evacuation of the inner container 26 may be required. If the leak is minor, maintenance operations may be performed in advance. Maintenance operations may include repairing the inner container 26 to repair the leak, replacing or desorbing hydrogen materials (if applicable), and re-evacuating the insulating chamber 29.

[0080] exist Figures 1 to 3 In the embodiment shown, the housing 27 comprises two separable parts 48 and 49. The first part 48 comprises an end and a body. The second part 49 comprises an opposite end. The first and second parts are sealed and detachably connected by two sealing rings 50 and 51, which provide metal / metal sealing surfaces by interference. The interference can be cone to cone, ring to cone or surface to surface, wherein, where applicable, the O-ring seal is made of a heat-mounted metal (especially made of a copper alloy) or an elastomer. The interference is provided by axial clamping (especially by bolts). The sealing rings 50 and 51 are annular.

[0081] exist Figure 4In the embodiment shown, the outer shell 27 is divided into several parts. The two parts are sealed by sealing rings 50 and 51, as described above. The parts of the inner container 26 can be standardized to accommodate various capacities, including the end, one or more central parts and the end with perforations for the neck. A plurality of support rings 35 can be provided.

[0082] exist Figure 5 In the embodiment shown, the chassis 30 of the housing 27 includes annular ribs 32, longitudinal members 33 parallel to the longitudinal axis, and diagonal struts. The housing 27 includes generally triangular panels 31, each of which is mounted between the ribs, longitudinal members and struts, and panels with dome-shaped ends. The triangular panels 31 allow the chassis 30 to be visible. The dome panels cover the chassis 30 beyond the ribs 32.

[0083] exist Figure 6 In the embodiment shown, the distribution circuit 1 comprises a first valve 11 for each cryogenic tank 2. The first valve 11 is mounted on the outlet pipe 4. The first valve 11 is controlled to an open position and a closed position. The intermediate position of the first valve 11 is dynamic, because the first valve 11 is in motion when passing through the intermediate position. In other words, the first valve 11 is of the all-or-nothing type. The first valve 11 can be arranged immediately downstream of the flow meter 22.

[0084] The first valve 11 is present in the cryogenic distributor 5. The cryogenic distributor 5 may comprise a common conduit 6 connecting the outlets of the first valve 11. The distributor is cryogenic because it passes liquid fuel / oxidant.

[0085] The cryogenic distributor 5 comprises a plurality of outlets, three in this case. A second valve 12 is mounted on each of the outlets. The second valve 12 is controlled to have an open position and a closed position. The intermediate position of the second valve 12 is dynamic, because the second valve 12 is in a moving state when passing through the intermediate position. In other words, the second valve 12 is of an all-or-nothing type. There are three second valves 12 here.

[0086] A central temporary storage tank 7 is installed downstream of each second valve 12. Three temporary storage tanks 7 are provided in this embodiment. Each temporary storage tank 7 also serves as a vaporizer. Insulation can be avoided. Each temporary storage tank 7 receives liquid and supplies gas downstream. Between filling and emptying, a pressure increase or a vaporization step occurs in each temporary storage tank 7. Each temporary storage tank 7 is capable of withstanding a maximum operating pressure of 300 bar to 1000 bar. Each temporary storage tank 7 is designed to operate in a temperature range of -253°C to +60°C. The temporary storage tank 7 is two-phase in some operating steps and a gaseous single phase in other operating steps. Each temporary storage tank 7 can be equipped with a heating element 8.

[0087] A third valve 13 is installed downstream of each temporary storage tank 7 to supply gas, and a pressure reducing valve 9 is installed downstream of the third valve 13. The pressure reducing valve 9 limits the pressure to supply gas at a consumption pressure determined by the manufacturer of the consumption element 3. The pressure reducing valve 9 is active when the pressure in the temporary storage tank is higher than the consumption pressure, and is otherwise inactive. The consumption pressure is lower than the maximum pressure of the temporary storage tank 7. The consumption pressure is independent of the maximum pressure of the cryogenic tank. The third valve 18 is of an all-or-nothing type.

[0088] Downstream of each pressure reducing valve 9, a controlled fourth valve 14 may be provided. The fourth valve 14 is of the all-or-nothing type.

[0089] Depending on the selected option, the fourth valve 14 or the pressure reducing valve 9 is present in the collector 10. The collector 10 may include a conduit connected to the outlet of the fourth valve 14 or the pressure reducing valve 9. The collector 10 conveys the gas. The collector 10 is connected downstream to a conduit 23 that supplies to the consumable member 3. Typically, a supply conduit 23 is provided for each consumable member 3. Each supply conduit 23 may be equipped with a controlled supply valve 24. The supply valve 24 has a variable flow rate.

[0090] The distribution circuit 1 comprises at least one compressor 20 connected to the collector 10. Typically, two compressors 20 are provided in parallel for redundancy. The compressor 20 is electric. The compressor 20 may be equipped with a controlled upstream valve. The compressor 20 discharges the gas into the collector 10. Specifically, in the case of a single consumer 3, the collector 10 consists of a conduit.

[0091] A fifth valve 15 is installed downstream of each temporary storage tank 7 to supply gas, and a second collector is installed downstream of the fifth valve 15. The second collector is connected to the compressor 20. The fifth valve 15 makes it possible to isolate the temporary storage tank 7 and the compressor 20. The fifth valve 15 is controlled. The fifth valve 15 is of an all or nothing type.

[0092] The compressor 20 increases the pressure to supply gas equal to the consumption pressure specified by the manufacturer of the consumable part 3. The consumption pressure is lower than the maximum pressure in the temporary storage tank 7. The compressor 20 makes it possible to take out gas from the temporary storage tank 7 at a pressure lower than the consumption pressure to supply the collector 10 and the consumable part 3. More thorough emptying of the temporary storage tank 7 makes it possible to increase the supply range of the gas contained in the temporary storage tank 7 or reduce the volume of the temporary storage tank 7.

[0093] The temporary storage tank 7 is emptied sufficiently to make the internal pressure of the temporary storage tank 7 lower than the pressure in one of the cryogenic storage tanks, so that during the filling after the evacuation, the liquid can be transferred from the cryogenic storage tank to the temporary storage tank 7 by the pressure difference. Therefore, the liquid in the cryogenic storage tank is sucked into the temporary storage tank 7 to achieve pressure balance. The cryogenic pump can be omitted, thereby saving mass and energy consumption.

[0094] The distribution circuit 1 provides a combination of individual states of each cryogenic storage tank, each temporary storage tank 7 and each consumable member 3. Multiple consumable members 3 can be active at the same time. In normal mode, one cryogenic storage tank is emptied, while the other cryogenic storage tanks are inactive and therefore closed. However, in some cases, for example, in order to reduce the pressure in multiple cryogenic storage tanks, a specific mode can be provided in which multiple cryogenic storage tanks are emptied. The temporary storage tank 7 has a filling mode, a gasification mode, a gas storage mode and an emptying mode.

[0095] When one of the cryogenic tanks is emptied, the corresponding first valve is opened, while the other first valve 11 is closed. When one of the consumable components 3 is supplied, the corresponding supply valve 24 is opened.

[0096] When one of the temporary storage tanks 7 is in the filling mode, the second valve 12 connected to the temporary storage tank 7 is opened, and at least one first valve 11 is opened. Except for the case of filling two temporary storage tanks 7 at the same time, the other second valves 12 are closed. The third valve 13 connected to the temporary storage tank 7 is closed. The fifth valve connected to the temporary storage tank 7 is closed.

[0097] When one of the temporary storage tanks 7 is in the gasification mode, the second valve 12 connected to the temporary storage tank 7, the third valve 13 connected to the temporary storage tank 7 and the fifth valve 15 connected to the temporary storage tank 7 are closed. The gasification mode lasts for a short time, especially when the ambient atmosphere is hot and / or the temporary storage tank 7 is heated.

[0098] When one of the temporary storage tanks 7 is in the emptying mode, the second valve 12 connected to the temporary storage tank 7 is closed. In the first part of the emptying, the pressure in the temporary storage tank 7 is higher than the consumption pressure. The third valve 13 connected to the temporary storage tank 7 is opened, the corresponding fourth valve 14 is opened, and the fifth valve connected to the temporary storage tank 7 is closed. The gas undergoes a pressure reduction in the pressure reducing valve 9 and is supplied to the collector 10 at the consumption pressure. The gas is then consumed by the consumption member 3.

[0099] At a given moment, of the three temporary tanks 7, one is in filling mode, another in vaporization and storage mode, and the third in emptying mode. Due to the different durations of these modes, it is also possible to find two temporary tanks 7 in filling mode and the third in emptying mode, or vice versa. It is also possible to find two temporary tanks 7 in storage mode and the third in emptying mode, or vice versa.

[0100] In this embodiment, a flow meter 22 is arranged at the outlet of each liquid fuel / oxidant source 2. The flow meter 22 enables the amount of liquid supplied to such a temporary storage tank 7 to be known with sufficient accuracy.

[0101] In this embodiment, the distribution circuit 1 comprises a control unit 25 which receives external commands, for example from a consumable component 3 outside the aircraft storage device or from a central control unit of the aircraft, and liquid flow rate data from the flow meter 22. The control unit 25 generates commands and sends them to the first, second, third, fourth and fifth controlled valves and the controlled supply valve 24. The commands can be "open" or "closed". The control unit 25 manages the combination of the various states.

[0102] In a variant, the first valve 11 can be replaced by at least one multi-way valve having multiple inlets and one outlet. In this case, it is advantageous to provide a multi-way valve with mixed positions, in particular to provide at least one position for simultaneously evacuating two or more cryogenic tanks 2 to reduce their pressure while avoiding leakage to the atmosphere.

[0103] In a variant, the second valve 12 may be replaced by at least one multi-way valve having one inlet and a plurality of outlets, one for each temporary tank 7. The multi-way valve forms a distributor.

[0104] In a variant, the pressure reducing valve 9 can be replaced by a single pressure reducing valve 9 in which the third valve 13 is located. In this case, the third valve 13 can be replaced by at least one multi-way valve having a plurality of inlets and an outlet leading to the pressure reducing valve. The fourth valve 14 is then replaced by a single fourth valve 14 which, where applicable, is not controlled.

[0105] In a variant, the fifth valve 15 may be replaced by at least one multi-way valve having a plurality of inlets, one for each temporary storage tank 7 , and an outlet to the compressor 20 or compressors 20 . The multi-way valve forms the collector 10 .

[0106] The cryogenic tank 2 is affected by the evaporation of the liquid, and a gas collection loop can be provided at the top of the cryogenic tank 2. The collection loop can be activated above the threshold pressure by a calibrated pressure valve. The collection loop includes a compressor for re-injecting the gas downstream, for example between the fifth valve 15 and the compressor 20.

[0107] Optionally, an additional flow meter is provided at the inlet of each buffer tank. This ensures redundancy of the liquid flow measurement.

[0108] The capacity of the cryogenic storage device is from 10 kg to 10,000 kg of gas, preferably from 100 kg to 10,000 kg of gas.

[0109] A temporary storage and gasification tank 7 is provided for raising the pressure of the gas supplied by the device. An upstream valve 12 is designed to be opened for liquid flow during the phase of filling the temporary storage tank 7 and to be closed outside the filling phase. At least one downstream valve 13, 15 is designed to be opened for gas flow during the phase of emptying the temporary storage tank 7 and to be closed outside the emptying phase. The upstream valve and the downstream valve are closed during the gasification phase. The upstream valve and the downstream valve have an all-or-nothing control. At least one compressor 20 is arranged downstream of the downstream valve 15. The compressor 20 is started at the end of the emptying phase so that the pressure value in the temporary storage tank 7 is lower than the pressure value in the device. A pressure reducing valve 9 is arranged downstream of the downstream valve. The pressure reducing valve 9 is started at the beginning of the emptying phase so that the gas pressure value at the outlet is lower than the pressure value in the temporary storage tank 7.

[0110] Rail, road or marine cryogenic gas storage tank, spherical or elongated, in particular spherical or elongated about a longitudinal axis, comprising an inner container defining a liquefied gas storage chamber 28, an outer shell 27 containing the inner container and made of a plurality of removable parts, the outer shell 27 being made of a material resistant to temperatures from below -60°C to at least +80°C, an insulating chamber 29 being defined between the inner container and the outer shell, the insulating chamber 29 being impermeable to helium equal to or better than 10-100°C under reduced pressure 9 mbar*l / s, an insulating chamber 29 is defined between the inner container and the outer shell, two connections, at least one sliding connection, supporting the inner container and carried by the outer shell, a support ring is installed between the inner container and the outer shell at a certain distance from the connection in the insulating chamber, a removable collector 38 sealingly passes through the outer shell and the inner container, and a thermally insulating flexible neck 42, forming a gas-tight interface between the collector 38 on the one hand and the outer shell and the inner container on the other hand, the neck 42 is arranged around a part of the collector 38, and the neck 42 passes through the insulating chamber so that the collector 38 can be removed independently of the pressure in the insulating chamber.

[0111] The storage and distribution assembly comprises a cryogenic tank for hydrogen storage, comprising an inner container defining a liquefied gas storage chamber, an outer shell accommodating the inner container, a gas-tight insulating chamber defined between the inner container and the outer shell, a removable liquefied gas collector sealingly passing through the outer shell and the inner container, the collector extending on a diameter or diagonal of the inner container and having a free end close to the bottom of the inner container, a liquefied gas conduit supplied by the collector, a temporary storage tank forming a gasification member for increasing the pressure of the gas supplied by the device, an upstream valve designed to be opened for liquid flow during a phase of filling the temporary storage tank and closed outside the filling phase, a downstream valve designed to be opened for gas flow during a phase of emptying the temporary storage tank and closed outside the emptying phase, the upstream valve and the downstream valve being closed during the gasification phase, the upstream valve and the downstream valve having an all-or-nothing control, and a pressure reducing valve arranged downstream of the downstream valve, the pressure reducing valve being active at the beginning of the emptying phase to make the gas pressure at the outlet lower than the pressure in the temporary storage tank.

[0112] The collector of the device is not suitable for withstanding high pressures, in particular high pressures above 10 bar. During the liquefied gas delivery, the pressure of the liquefied gas in the cryogenic tank, in particular in the pipe 39 of the collector, and in the outlet pipe 4 is substantially the same. Outside of refined gas delivery, the pressure of the liquefied gas in the cryogenic tank, in particular in the pipe 39 of the collector, and in the outlet pipe 4 is the same. The device has no pump. The liquefied gas can be decanted by the pressure difference between the cryogenic tank and the downstream components.

[0113] The tube 39 may consist of a tube emerging from the outlet duct 4 .

[0114] Each temporary storage tank 7 forms a vaporizer. Each temporary storage tank 7 forms a heat exchanger. Each temporary storage tank 7 forms a heat exchanger comprising at least one cryogenic liquid inlet and at least one gas outlet. The temporary storage tank 7 has no thermal insulation layer. The temporary storage tank 7 comprises a simple outer shell. The temporary storage tank 7 is made of metal and / or composite material. The temporary storage tank 7 is made of conductive material in whole or in part. The temporary storage tank 7 can withstand low temperatures. Compared with the low-pressure cryogenic storage tank, the temporary storage tank 7 can withstand high working pressure. Compared with the cryogenic storage tank 2 having a long storage life, the temporary storage tank 7 has a short storage life.

[0115] exist Fig. 9 In the embodiment of the present invention, the neck 42 has an outer surface 44 having circular annular corrugations 64. The outer surface 44 is wavy. Figure 7 In comparison, the developed length of the corrugation 64 is greater than the length of the chevron, so better insulation can be achieved by lengthening the conduction path.

[0116] exist Fig.10In the embodiment of the present invention, the tube 49 is made of several parts, which together form a tube for discharging liquefied gas. The tube 39 includes a bottom 65 mainly arranged in the storage chamber 28, an intermediate sleeve 66 arranged in the plug 41 and a top 67 facing the outside. The bottom 65 is formed by a metal conduit, for example, made of stainless steel. The bottom 65 is inserted into the plug 41 through the top. The top 67 is formed by a metal conduit, for example, made of stainless steel. The top 67 is inserted into the plug 41 through the bottom end. The bottom 65 is away from the top 67. The intermediate sleeve 66 is contained in the plug 41. The intermediate sleeve 66 is made of a material with a thermal conductivity lower than the thermal conductivity of the bottom 65 and lower than the thermal conductivity of the top 67. The intermediate sleeve 66 can be made of a resin resistant to low temperatures, such as epoxy resin. The intermediate sleeve 66 surrounds the top of the bottom 65. The intermediate sleeve 66 surrounds the bottom end of the top 67. The heat loss is low.

[0117] The tube of the vent 53 is made in a similar manner to the tube 39, with several portions having different thermal properties, particularly in terms of conduction, to reduce heat losses. The length of the bottom 65 of the tube of the exhaust 53 is less than the length of the bottom 65 of the tube 39. The middle sleeve 66 of the tube of the exhaust 53 can be the same as the middle sleeve 66 of the tube 39. The top 67 of the tube of the exhaust 53 can be the same as the top 67 of the tube 39.

[0118] The angle of the annular chevron relative to the radial plane is less than Figure 6 The angle of the annular chevron relative to the radial plane is therefore less than 45°. The angle may be between 5° and 30°. The annular chevron has branches that undulate around the conical base. The conductive path is extended. In a variant, there is also provided a formation such as Figure 6 The symmetrical herringbone shape of the teeth 44 or Fig. 9 on the undulating surface.

Claims

1. An aircraft cryogenic gas storage tank device, installed on an aircraft, having a generally elongated shape with rounded ends and a circular, spherical or annular shape around an axis, comprising: an inner container (26) defining a liquefied gas storage chamber (28); an outer shell (27) which accommodates the inner container (26); A reduced pressure insulation chamber (29) is defined between the inner container (26) and the outer shell (27), wherein the sealing performance of the reduced pressure insulation chamber is equal to or better than 10 -9 mbar*l / s; A removable collector (38) which passes through the outer shell (27) and the inner container (26) in a sealed manner; the collector (38) extends on a diameter or diagonal of the inner container (26) and has a free end close to the bottom of the inner container (26); and a conduit supplied by the collector (38), the aviation cryogenic gas storage tank device comprising a thermally insulating flexible neck (42) which forms an airtight interface between the collector (38) on the one hand and the outer shell (27) and the inner container (26) on the other hand, the neck (42) being arranged around a portion of the collector (38), the neck (42) passing through the insulating chamber (29) so that the collector (38) can be removed independently of the pressure in the reduced pressure insulating chamber (29).

2. The apparatus of claim 1, comprising a thermal plug assembly removably mounted on the collector (38) and accessible from the exterior of the aviation cryogenic gas storage tank.

3. The device according to claim 1, comprising a support ring (35) mounted between the inner container (26) and the outer shell (27).

4. The device according to claim 1 comprises a connector (34), the connector comprising an axial concave surface in the outer shell (27) for receiving and supporting an axial protrusion of the inner container, and the device comprises a shell supporting the outer shell (27) and surrounding the connector.

5. The device according to claim 1, wherein: The neck (42) has an outer surface (44) with an annular chevron shape.

6. The device according to claim 1, wherein: The neck (42) has a wavy outer surface (44).

7. The device according to claim 1, wherein: The housing (27) includes a chassis (30), a sealing panel (31), and a gasket for bearing the pressure between the chassis (30) and the panel (31) and / or between multiple panels (31), and the chassis (30) includes ribs (32) and longitudinal members (33).

8. The device according to claim 1, comprising an anti-sway member in the inner container and a reinforcing rib in the inner container, wherein the reinforcing rib is preferably a support or a tie rod.

9. The device according to claim 1, wherein: A hydrogen absorbing material (46) is arranged in the insulating chamber (29), and a hydrogen presence detector (47) is installed in the insulating chamber (29).

10. Assembly, comprising a device according to any one of claims 1 to 9, a temporary storage tank (7) forming a gasification component for increasing the pressure of the gas supplied by the device, an upstream valve (12) designed to open for liquid flow during the stage of filling the temporary storage tank (7) and to be closed outside the filling stage, a downstream valve (13, 15) designed to open for gas flow during the stage of emptying the temporary storage tank (7) and to be closed outside the emptying stage, the upstream valve and the downstream valve being closed during the gasification stage, the upstream valve and the downstream valve having an all-or-nothing control, and a compressor (20) arranged downstream of the downstream valve (15), the compressor (20) being started at the end of the emptying stage to reduce the pressure value in the temporary storage tank (7) to a lower value than the pressure value in the device, and a pressure reducing valve (9) arranged downstream of the downstream valve, the pressure reducing valve (9) being started at the beginning of the emptying stage to reduce the gas pressure at the outlet to a value lower than the pressure in the temporary storage tank (7).

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